Begell House Inc.International Journal of Energetic Materials and Chemical PropulsionIJEMCP2150-766X1132012HIGH EXPLOSIVE THERMODYNAMIC EQUATIONS OF STATE CALIBRATION FOR BROAD APPLICATION197-208GregoryStunzenasU.S. Army Armament Research, Development, and Engineering Center, Picatinny, NJ, 07806, USAErnest LBakerU.S. Army Armament Research, Development and Engineering Center (ARDEC), Picatinny, New Jersey 07806-5000, USALeonard I. StielNYU Polytechnic School of Engineering, Six Metrotech Center, Brooklyn, New York 11201, USAD. J. MurphyU.S. Army Armament Research, Development and Engineering Center (ARDEC), Picatinny, New Jersey 07806-5000, USAAdamEneaU.S. Army Armament Research, Development, and Engineering Center, Picatinny, NJ, 07806, USAWork was conducted to optimize the calibration of the parameters to match cylinder test and blast overpressure experimental data. The Arbitrary Lagrangian Eulerian Hydrocode (ALE3D) was used as a method of modeling various explosives using the Jones−Wilkins−Lee−Baker (JWLB) parameters obtained from the JAGUAR thermochemical predictions. The peak pressure and impulse results of the model were compared to those obtained from tests conducted on the Free Field Blast Pad located at Eglin Air Force Base.A NOVEL HYBRID BINDER SYSTEM FOR EXTRUDABLE COMPOSITE PROPELLANT209-220V. D. DeuskarHigh Energy Materials Research Laboratory, Sutarwadi, Pune, IndiaK. S. MulageHigh Energy Materials Research Laboratory, Sutarwadi, Pune-411 021, IndiaA. K. MishraHigh Energy Materials Research Laboratory, Sutarwadi, Pune-411 021, IndiaR. N. PatkarHigh Energy Materials Research Laboratory, Sutarwadi, Pune-411 021, IndiaS. H. KharatHigh Energy Materials Research Laboratory, Sutarwadi, Pune-411 021, IndiaSeema DilipKakadeHigh Energy Materials Research Laboratory, Pune, 411021, IndiaExtrudable composite propellant is an entirely new thrust area in the development of composite propellants. These are based on high-density thermoplastic elastomer as a propellant binder with ammonium perchlorate as an oxidizer and aluminum as a metallic fuel. The present paper reports the evaluation of a combination of binders (Irostic, a thermoplastic polyurethane, and Viton, a fluoropolymer) as a binder for extrudable composite propellant. Both polymers were completely characterized before use. The feasibility of propellant processing was studied and processing parameters such as the rolling temperature, number of passes, extrusion temperature, and pressure have been established. The propellant formulations were characterized for burning rate, density, mechanical properties, and thermal analysis. The results reveal that as the Irostic content increases the density decreases and the mechanical properties (i.e., the tensile strength and percentage of elongation) increase. Due to the energetic nature of Viton, the burn rates are on the higher side for the composition containing Viton as binder compared to the Irostic-based composition. The details of propellant processing, characterization, and thermal analyses are presented.SYNTHESIS, CHARACTERIZATION, AND REACTION KINETICS OF NANO-STRUCTURED Mg−V−Ni COMPOSITES FOR SOLID-STATE HYDROGEN STORAGE221-240K. G. BambhaniyaElectrical Research and Development Association, ERDA Road, Makarpura, Vadodara 390 010, IndiaG. S. GrewalElectrical Research and Development Association, ERDA Road, Makarpura, Vadodara 390 010, IndiaVagishShrinetElectrical Research and Development Association, ERDA Road, Makarpura, Vadodara 390 010, IndiaN. L. SinghPhysics Department, Faculty of Science, The Maharaja Sayajirao University of Baroda, 390 002, IndiaT. P. GovindanElectrical Research and Development Association, ERDA Road, Makarpura, Vadodara 390 010, IndiaIn this study, we have developed and characterized various Mg−V−Ni compositions with respect to hydrogen storage. The study was conducted using magnesium as the base material with additions of 5 atomic% of nickel and vanadium in the range of 2.5−10 atomic%. The various compositions were synthesized using high-energy ball milling with different milling times. The compositions were characterized using scanning electron microscopy, energy-dispersive X-ray spectrometry, and X-ray diffraction, and the hydriding−dehydriding characteristics studied using the Sievert method. It was found that the maximum reversible hydrogen storage capacity in the Mg−V−Ni system is 5.71 mass %. Furthermore, it was found that 6 mass% of hydrogen is absorbed within the first 5 min at 210° C. This lowered hydriding temperature is associated with the presence of vanadium as a catalyst. The hydriding enthalpy of the optimized (highest storage capacity) Mg−V−Ni composition has been measured using differential scanning calorimetry as 79.15 ± 3.56 kJ/mol of H2 and the hydriding entropy was obtained as 141.18 ± 6.35 J/mol of H2 K.HYDROXYLAMMONIUM NITRATE AS GREEN PROPELLANT: DECOMPOSITION AND STABILITY241-257RachidAmrousseInstitute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA), 3-1-1 Yoshinodai, Chuo-Ku, Sagamihara, Kanagawa 252-5210, JapanToshiyukiKatsumiDepartment of Mechanical Engineering, Nagaoka University of Technology, JapanT. SulaimanJAXA, Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-Ku, Sagamihara, Kanagawa 252-5210, JapanB. R. DasJAXA, Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-Ku, Sagamihara, Kanagawa 252-5210, JapanH. KumagaiDepartment of Chemical System Engineering, University of Tokyo, 7-3-1 Hongo, Bunkyo-Ku, Tokyo 113-8656, JapanK. MaedaDepartment of Chemical System Engineering, University of Tokyo, 7-3-1 Hongo, Bunkyo-Ku, Tokyo 113-8656, Japan; Precursory Research for Embryonic Science and Technology, Japan Science and Technology Agency, 4-1-8 Honcho Kawaguchi, Saitama 332-0012, JapanKeiichiHoriInstitute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA), 3-1-1 Yoshinodai, Chuo-Ku, Sagamihara, Kanagawa 252-5210, JapanBinary hydroxyl ammonium nitrate (HAN) aqueous mixtures have been prepared. Four series of ternary mixtures have been synthesized with methanol and ethanol as fuels: two series with HAN excess and two other series with stoichiometric fuel contents. Thermal and catalytic decomposition of the prepared solutions have been analyzed. For binary HAN solutions, the thermal decomposition starts only once water has been fully vaporized and the oxidizer is in the liquid state. The influence of the fuel depends strongly on the oxidizer. Methanol and ethanol are vaporized before the decomposition, leading to results close to those observed for binary mixtures. HAN and HAN-fuel-based solutions display the highest catalytic effect with a temperature decrease of about 100° C.COMBUSTION OF BIMODAL ALUMINUM PARTICLES AND ICE MIXTURES259-273Terrence L. Connell, Jr.Department of Mechanical and Nuclear Engineering, The Pennsylvania State University, University Park, Pennsylvania 16802, USAGrant A.RishaThe Pennsylvania State University-Altoona, Altoona, Pennsylvania 16601,
USARichard A.YetterThe Pennsylvania State University, University Park, Pennsylvania 16802,
USAVigorYangDepartment of Mechanical Engineering The Pennsylvania State University University Park, PA 16802, USA; School of Aerospace Engineering, Georgia Institute of Technology, Atlanta, Georgia 30332, USASteven F.SonSchool of Mechanical Engineering, Purdue University, West Lafayette, Indiana 47907, USAThe combustion of aluminum with ice is studied using various mixtures of nano- and micrometer-sized aluminum particles as a means to generate high-temperature hydrogen at fast rates for propulsion and power applications. Bimodal distributions are of interest in order to vary mixture packing densities and nascent alumina concentrations in the initial reactant mixture. In addition, the burning rate can be tailored by introducing various particle sizes. The effects of the bimodal distributions and equivalence ratio on ignition, combustion rates, and combustion efficiency are investigated in strand experiments at constant pressure and in small lab-scale [1.91 cm (0.75 in.) diameter] static fired-rocket-motor combustion chambers with center-perforated propellant grains. The aluminum particles consisted of nanometer-sized particles with a nominal diameter of 80 nm and micron-sized particles with nominal diameters of 2 and 5 µm. The micron particle addition ranged from 0% to 80% by active mass in the mixture. Burning rates from 1.1 (160 psia) to 14.2 MPa (2060 psia) were determined. From the small scale motor experiments, thrust, C*, Isp, and C* and Isp efficiencies are provided. From these results, mechanistic issues of the combustion process are discussed. In particular, overall lean equivalence ratios that produce flame temperatures near the melting point of alumina resulted in considerably lower experimental C* and Isp efficiencies than equivalence ratios closer to stoichiometric. The substitution of micron aluminum for nanometer aluminum had little effect on the linear burning rates of Al/ice mixtures for low-mass substitutions. However, as the mass addition of micron aluminum increased (e.g., beyond 40% 2-µm aluminum in place of 80-nm aluminum), the burning rates decreased. The effects of bimodal aluminum compositions on motor performance were minor, although the experimental results suggest longer combustion times are necessary for complete combustion.ON GAS RELEASE BY THERMALLY-INITIATED FULLY-DENSE 2Al·3CuO NANOCOMPOSITE POWDER275-292Rayon A. WilliamsNew Jersey Institute of Technology, Newark, New Jersey, 07102, USA MirkoSchoenitzNew Jersey Institute of Technology, Newark, New Jersey 07102, USAAlexandre ErmolineNew Jersey Institute of Technology, Newark, New Jersey, 07102, USA Edward L.DreizinNew Jersey Institute of Technology, Newark, New Jersey 07102, USA; Tomsk State University, Tomsk, 634050, RussiaA recently developed model for low-temperature exothermic reactions in nanocomposite Al-CuO thermites described the evolution of an alumina layer growing between Al and CuO and changes in its diffusion resistance as critically affecting ignition of the composite reactive material. The model was successful in describing ignition of individual composite particles in a CO2 laser beam. However, it was unable to conclusively predict ignition of the same powder particles coated onto an electrically heated filament. In this work, ignition of fully-dense 2Al·3CuO nanocomposite powder prepared by arrested reactive milling was studied using a modified electrically heated filament experiment, located in a miniature vacuum chamber. Thin layers of the powders coated on a nickel-chromium filament were ignited at heating rates between 200 and 16,000 K/s. The ignition was accompanied by both optical emission and pressure signals. The pressure signals occurred before emission, with increasing delay at higher heating rates. Ignition temperatures were only slightly affected by the heating rate. The results are interpreted proposing that the low-temperature redox reaction produces a metastable CuOl−x phase with 0 < x ≤ 1 which releases oxygen upon heating. It is shown that despite a relatively small heat release, the low-temperature reactions in nanocomposite thermites are important as producing destabilized, partially reduced oxides that decompose with gas release upon heating. In the present experiments, the gas release changed thermal properties of the powder coating, reducing the efficiency of heat exchange with the supporting filament and thus enabling its thermal runaway and ignition.